Space Qualification
PREPARING THE SATELLITES FOR TOUGH MISSIONS
At EnduroSat we strongly believe in the endurance of our systems. Testing at the extremes and verifying the performance at the limit demonstrates the capabilities of our CubeSats. All modules are tested fully integrated in a 1.5U and 3U CubeSat platforms.
EnduroSat performs the qualification test campaign of all its modules in the Space Qualification Laboratory of the Italian Aerospace Research Centre (CIRA).
ENDUROSAT CubeSat platform underwent full campaign of tests at qualification level exceeding the standard requirements for this class of satellites
Functional Test
During the space qualification campaign, EnduroSat CubeSats underwent high level of functional tests to demonstrate the integrity of the system. All modules were performing at their nominal level.
The tests were performed following the strict specifications of the ESA ECSS-E-ST-10-03C and NASA GEVS: GSFC-STD-7000A standards.

Physical Properties
Awareness of space environment Accurate determination of the physical properties:
- Weight: all subsystems (modules) and fully assembled CubeSat platform
- Center of Gravity (CoG): Fully assembled CubeSat platform
- Moment of Inertia (MoI): Fully assembled CubeSat platform
Thermal Cycling
The purpose of thermal cycling test is to demonstrate that the systems are able to survive, without loss of integrity or functionality, the thermal loads experienced during the space mission.
- min Temp -30°C
- max Temp +65°C
- Temperature Variation rate ≥1°C/min
- dwell time 1h at extreme levels
- 8 cycles
Thermal Vacuum
The purpose of thermal vacuum test (TVAC) is to demonstrate that the systems are able to survive, without loss of integrity or functionality, the thermal and pressure conditions experienced in the space environment. To reach deep vacuum conditions (as high as 10-7 mbar during the cold cycle), a bakeout of the systems was performed in order to minimize the outgassing during the TVAC test:
- Vacuum between 10-5 and 10-6 mbar
- Chamber Temperature =50 °C.
- Dwell Time = 2 h.
- Vacuum between 10-6 and 10-7 mbar
- Minimum temperature: -30 °C
- Maximum temperature: 65 °C
- Temperature variation rate ≥ 1 °C/min
- Dwell time 1h at extreme levels
- Number of cycles: 8
Sinusoidal vibration
The purpose of the mechanical tests is to demonstrate that the primary structure and all electronic and mechanical components can withstand the vibrations and the loads experienced during launch and deployment.
The tests were performed following the NASA GEVS: GSFC-STD-7000A standard:
- Duration: sine sweep at 2 Oct/min, 5 Hz – 140 Hz;
- Repetitions: 3 times for each orthogonal axes;
- Qualification test level:
Frequency (Hz) | Amplitude (g) |
---|---|
5-100 | 2.5 |
100-140 | 1.25 |
Random Vibration
- Duration: 2 minutes for each test;
- Repetitions: 3 times for each orthogonal axes;
- Qualification test level
Frequency (Hz) | ASD level (g2/Hz) |
---|---|
20 | 0.026 |
20-50 | +6dB/oct |
50-800 | 0.16 |
800-2000 | -6dB/oct |
2000 | 0.026 |
Overall | 14.1 Grms |
Pyroshock Test
The shock test was performed using a proprietary pyroshock facility.
- Repetitions: 3 times each for orthogonal axes;
- Qualification test level
Frequency (Hz) | SRS (g) |
---|---|
30 | 5 |
100 | 100 |
700 | 1500 |
1000 | 2400 |
1500 | 4000 |
5000 | 4000 |
10000 | 2000 |